Continuously variable turbine

ABSTRACT

A compressor includes an assembly with a case body defining a chamber, a shaft defining a rotational axis, a ring piston positioned within the chamber, a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft, and a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber.

RELATED APPLICATION

The present application is a continuation-in-part of U.S. patentapplication Ser. No. 16/014,339, filed on Jun. 21, 2018, which claimsthe benefit of U.S. Provisional Patent Application No. 62/524,822, filedon Jun. 26, 2017.

The entire contents of the above-referenced applications areincorporated herein by reference.

INTRODUCTION

The present disclosure relates to a continuously variable turbine.

A turbine is a rotary device that extracts energy from a fluid andconverts it into useful work. Many types of turbines have been developedin the past. Various types of turbines include steam turbines, windturbines, gas turbines and water turbines.

In some turbines, a set of blades or vanes are positioned about a shaftor spindle. The blades or vanes are arranged such that flow of fluidthrough the blades or vanes causes the blades or vanes to move therebycausing the shaft or spindle to rotate. The turbine may be connectedmachinery such as a pump, compressor or components of a propulsionsystem. The work produced by the turbine can be utilized for generatingpower when coupled with a generator or producing thrust, for example,from jet engines.

While current turbines achieve their intended purpose, there is a needfor a new and improved turbine with higher efficiencies.

SUMMARY

According to several aspects, a compressor includes an assembly with acase body defining a chamber, a shaft defining a rotational axis, a ringpiston positioned within the chamber, a rotor assembly positioned withinthe ring piston, the rotor assembly being mounted on the shaft, and apair of opposed compression vanes, each compression vane having a sealcomponent with a surface that matches an outer curvature of the ringpiston to form a continuous surface seal between the seal component andthe ring piston as the rotor assembly and the ring piston rotate aboutthe axis of the shaft, the position of the continuous surface seals inthe chamber defining a first sub-chamber and a second sub-chamberbetween the surface seals, the case body further including an inlet portand an exhaust port for each sub-chamber.

In an additional aspect of the present disclosure, the compressor isconfigured to be staged with one or more additional compressors on theshaft.

In another aspect of the present disclosure, the staged compressorsprovide maximum fluid flow or maximum flow pressure depending upon theof the arrangement of the connections between the inlet ports and theoutlet ports.

In another aspect of the present disclosure, the staged compressors areconfigured to operate as an air motor for an input of high air flow rateat low pressure or low air flow rate at high pressure.

In another aspect of the present disclosure, the staged compressorsoperate as both motors and compressors on the single rotational axisdefined by the shaft to utilize a kinetic, pneumatic or hydraulic energysource to generate a pneumatic or hydraulic output, as well as a kineticoutput.

In another aspect of the present disclosure, the inlet port is definedby an assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reedvalve made of a thin, flexible material.

In another aspect of the present disclosure, the outlet port is definedby an assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reedvalve made of a thin, flexible material.

In another aspect of the present disclosure, an inner surface or anouter surface or both the inner surface and the outer surface of thering piston are coated with a material made of nano-particles to providelubrication-less operation of the compressor.

According to several aspects, an assembly includes a plurality ofcompressors. Each compressor includes an assembly with a case bodydefining a chamber, a shaft defining a rotational axis, a ring pistonpositioned within the chamber, a rotor assembly positioned within thering piston, the rotor assembly being mounted on the shaft, and a pairof opposed compression vanes, each compression vane having a sealcomponent with a surface that matches an outer curvature of the ringpiston to form a continuous surface seal between the seal component andthe ring piston as the rotor assembly and the ring piston rotate aboutthe axis of the shaft, the position of the continuous surface seals inthe chamber defining a first sub-chamber and a second sub-chamberbetween the surface seals, the case body further including an inlet portand an exhaust port for each sub-chamber. The compressors are configuredto be staged with one or more additional compressors on the shaft torotate about the rotational axis.

In another aspect of the present disclosure, the staged compressors areconfigured to operate as an air motor for an input of high air flow rateat low pressure or low air flow rate at high pressure.

In another aspect of the present disclosure, the staged compressorsoperate as both motors and compressors on the single rotational axisdefined by the shaft to utilize a kinetic, pneumatic or hydraulic energysource to generate a pneumatic or hydraulic output, as well as a kineticoutput.

In another aspect of the present disclosure, the inlet port is definedby an inlet assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reedvalve made of a thin, flexible material.

In another aspect of the present disclosure, the outlet port is definedby an outlet assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reedvalve made of a thin, flexible material.

In another aspect of the present disclosure, an inner surface or anouter surface or both the inner surface and the outer surface of thering piston are coated with a material made of nano-particles to providelubrication-less operation of the compressor.

Further areas of applicability will become apparent from the descriptionprovided herein. It should be understood that the description andspecific examples are intended for purposes of illustration only and arenot intended to limit the scope of the present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

The drawings described herein are for illustration purposes only and arenot intended to limit the scope of the present disclosure in any way.

FIG. 1 is a top view of a continuously variable turbine in accordancewith the principles of the present disclosure;

FIG. 2 is an exploded view of the turbine shown in FIG. 1;

FIG. 3 is a perspective view of a valve assembly for the turbine shownin FIG. 1;

FIG. 4 is a side view of the valve assembly shown in FIG. 3;

FIG. 5 illustrates two valve assemblies;

FIG. 6 is an exploded view of the valve assemblies and a ring piston ofthe turbine shown in FIG. 1;

FIG. 7 is a perspective view of a rotor assembly for the turbine shownin FIG. 1;

FIG. 8 is an exploded view of a multi-stack turbine in accordance withthe principles of the present disclosure;

FIG. 9 shows the turbine of FIG. 1 operating as a compressor;

FIG. 10 shows the turbine of FIG. 1 operating as a motor;

FIG. 11 shows a thermal engine with two of the turbines shown in FIG. 1in accordance with the principles of the present disclosure;

FIG. 12A is a perspective view of a rotor assembly for a compressor inaccordance with the principles of the present disclosure;

FIGS. 12B and 12C are side view of the rotor assembly shown in FIG. 12A;

FIG. 13A is a perspective view of a rotary piston for a compressor inaccordance with the principles of the present disclosure;

FIG. 13B is a side view of the rotary piston shown in FIG. 13A;

FIG. 13C is a view of the rotary piston taken from 13C-13C of FIG. 13B;

FIG. 14A is a perspective frontal view of a compression vane for acompressor in accordance with the principles of the present disclosure;

FIG. 14B is a perspective rear view of the compression vane for acompressor in accordance with the principles of the present disclosure;

FIG. 15A is a perspective view of an exhaust port assembly for acompressor in accordance with the principles of the present disclosure;

FIG. 15B is a view of an interface slot of the exhaust port assemblyshown in FIG. 15A;

FIG. 15C is a view of an exhaust port of the exhaust port assembly shownin FIG. 15A;

FIG. 15D is a view of the exhaust port assembly taken along the lines15D-15D of FIG. 15C;

FIG. 16A is a perspective view of an inlet port assembly for acompressor in accordance with the principles of the present disclosure;

FIG. 16B is a view of an interface slot of the inlet port assembly shownin FIG. 16A;

FIG. 16C is a view of an inlet port of the inlet port assembly shown inFIG. 16A;

FIG. 16D is a view of the inlet port assembly taken along the lines16D-16D of FIG. 16C;

FIG. 17A is a perspective view of a compressor in accordance with theprinciples of the present disclosure;

FIG. 17B is a side view of a face of the compressor shown in FIG. 17A;

FIG. 17C is an edge view of the compressor shown in FIG. 17A;

FIG. 17D is a view of the compressor taken along the line 17D-17D ofFIG. 17C; and

FIG. 17E is a perspective view of multiple staged compressors inaccordance with the principles of the present disclosure.

DETAILED DESCRIPTION

The following description is merely exemplary in nature and is notintended to limit the present disclosure, application, or uses.

Referring to FIGS. 1 and 2, there is shown a continuously variableturbine 10. The turbine 10 includes a rotor assembly 11, a valveassembly 29 and a case assembly 40. The case assembly 40 includes a casebody 40 with chamber 45. The rotor assembly 11 includes a ring piston 14positioned in the chamber 45 and a rotor body 12 mounted on a shaft 19and positioned within the ring piston 14.

Referring also to FIG. 7, a set of bearing shafts 17 extend throughrespective bearing holes 17 in the rotor body 12. A pair of bearings 16are mounted on each bearing shaft 17. Note that the present disclosureis not limited to the use of two bearings on each shaft. In someconfigurations, a single bearing 16 may be mounted on each shaft 17,while in other configurations, three or more bearings 16 may be mountedon each shaft 17.

As shown in FIG. 1, each pair of bearings 16 makes contact with theinner surface of the ring piston 14 such that there are three contactregions between the rotor body 12 and the inner surface of the ringpiston 14. Two of the bearing shafts 18 are positioned further away froman axis of rotation extending through the shaft 19 than the third shaft18. Accordingly, as the rotor body 12 rotates concentrically about theaxis of rotation, the piston ring 14 rotates eccentrically about theaxis of rotation.

The case assembly 40 includes a pair of manifolds 41 as shown in FIG. 6.Each valve assembly 29 includes a valve body 30 positioned in a slot 32of a respective manifold 41. As shown in FIGS. 3, 4 and 5, the valveassembly 29 further includes a pair of valve shafts 37 that extendthrough the manifold 41 and engage with retainers 34. A spring 33 ispositioned about each valve shaft 37 between eh valve body 30 and theretainer 34, and the shafts 37 are able to reciprocate in respectivechannels 36 in the valve body 30. Accordingly, as the valve body 30reciprocates outwardly and inwardly in the slot 32 relative to the axisof rotation of the shaft 19, the valve shafts 32 reciprocate in thechannels 36 causing the springs 33 to compress and expand. A bottomplate 43 and a top plate 44 are matted and secured to the case body 41to enclose the rotor assembly 11 and the valve assemblies 29 in the casebody 41. The shaft 19 can extend through an opening in either or boththe bottom plate 43 and the top plate 44. For example, as shown in FIG.2, the shaft 19 extends through the bottom plate 43 while a bearing capis employed to cover the opening in the top plate 44.

The valve assembly 29 also includes a seal component 31 attached to theseal body 30. Each seal component 31 has a curved surface or face 37that corresponds to or matches the curvature of the outer surface of thering piston 14. The springs 33 are pre-loaded so that there iscontinuous contact between the seal component 31 and the ring piston 14as the ring piston 14 rotates eccentrically about the axis of rotationof the shaft 19. The seal component 31 articulates relative to the sealbody 30. That is, the seal component 31 is able to move relative to theseal body 30 to fill the gaps 38 shown in FIG. 4 to ensure there is acontinuous surface seal between the curved face 37 of the seal component31 and the ring piston 14.

Each manifold 41 includes an intake port 48 and an exhaust port 49. Theposition of the surface seals formed by the seal components 31 definesub-chambers 45 a and 45 b. The robustness of the surface seals formedby the seal components 31 allow the sub-chambers 45 a and 45 b towithstand working pressures up to about 3000 psi without damaging orcompromising the surface seals. Each valve body 30 includes a flowchannel 35 to allow each chamber 45 a and 45 b to communicate withrespective intake and exhaust ports 48 and 49.

The various components of the turbine can be made from any suitablematerial, such as, for example, metals and plastics. The metals can beselected, for example, from any combination of aluminum, steel, andtitanium. In particular, the seal component 31 can be made fromsilicone.

Depending upon its use, a single turbine 10 can be employed or two ormore turbine can be stacked together for higher output capabilities. Forexample, two turbines 10 are shown in a staked arrangement in FIG. 8. Inthis configuration, a single bottom plate 43 is employed as a dividerbetween the two turbines 10, and a pair of top plates 44 are employed toencase the two rotor assemblies 11 and the two valve assemblies 29 intheir respective case bodies 41.

Turning now to FIG. 9, there is shown the turbine 10 utilized as acompressor. Specifically, as the shaft 19 is rotated (for example, by amotor), the rotor assembly 12 and the ring piston 14 rotate about theaxis of rotation of the shaft 19. Accordingly, inlet fluid 50 a is drawninto the sub-chamber 45 a though its respective intake port 48 a. Thefluid is compressed as the ring piston 14 rotates clockwise such thathigh pressure fluid 52 a is exhausted through the exhaust port 49 aassociated with the sub-chamber 45 a. Similarly, inlet fluid 50 b isdrawn into the sub-chamber 45 b through its intake port 48 b. The fluidis compressed such that high pressure fluid 52 b is exhausted throughthe exhaust port 49 b associated with the sub-chamber 45 b.

The turbine 10 can also be utilized as a motor as shown in FIG. 10. Inthis arrangement, high pressure fluid 60 a and 60 b are injected throughthe intake ports 48 a and 48 b into the respective sub-chambers 45 a and45 b. The expansion of the fluid cause the rotor body 12 and the ringpiston 14 to rotate clockwise such that the expanded fluid 62 a isexhausted from the sub-chamber 45 a and the expanded fluid 62 b isexhausted from the sub-chambers 45 b through the exhaust ports 49 a and49 b, respectively. Rotation of the rotor body 12 generates a torque onthe shaft 19, which can be connected to any suitable device that canutilize the output torque from the turbine 10.

In another configuration, multiple turbines 10 can be utilized in athermal engine 200 as shown in FIG. 11. The thermal engine 200 includesa cooling unit 202, a thermal exchange unit 204 that transfers heat tothe cooling unit 202, a pump 10A that receives cooled fluid from thethermal exchange unit 204, a heating unit 206 that receives the cooledfluid from the pump 10A, and an expander 10B that receives high pressureheated fluid from the heating unit 206 and transmits low pressure heatedfluid to the thermal exchange unit 204.

Both the pump 10A and the expander 10B are the same as theaforementioned turbine 10. Each is sized according to their desiredfunction and operation. Each of the pump 10A and the expander 10B may bea single turbine, or each or both may be a multi-stacked turbinedescribed previously. In operation, the pump 10A receives the cooledfluid from the thermal exchange unit 204 through a fluid line 214. Thepump 10A receives the fluid through the intake ports 48 a and 48 b andpumps the fluid out of the respective sub-chambers 45 a and 45 b intothe fluid line 218 via the exhaust ports 49 a and 49 b. The fluid istransmitted through the fluid line 218 to the thermal heating unit 206where the fluid is heated. The high pressure heated fluid is transmittedfrom the thermal heating unit 206 to the expander 10A through fluidlines 220.

The high pressure heated fluid enters into the sub-chambers 45 a and 45b of the expander 10B through the intake ports 48 a and 48 b,respectively. The expanded fluid leaves the sub-chambers 45 a and 45 bthrough the exhaust ports 49 a and 49 b and is transmitted to thethermal exchange unit 204. The rotation of the rotor body 12 of theexpander 10B generates torque than can be transmitted via the shaft 19to any desired machinery coupled to the shaft 19.

The thermal exchange unit 204 transfers the heat in the fluid from theexpander 10B into the fluid circulating in fluid lines 212 and 213. Morespecifically, a circulation pump 208 draws the fluid from the thermalexchange unit 204 through the fluid line 212 and transmits it to thecooling unit 202. The cooled fluid is then pumped back to the thermalexchange unit 204 through the fluid line 213.

Note that the fluid flowing through the fluid lines 212 and 213 definesa first closed circuit of fluid flow, and the fluid flowing through thefluid lines 214, 218, 220 and 216 defines a second closed circuit offluid flow. A control unit 210 may be utilized to control the operationof the thermal engine 200.

Referring now to FIGS. 17A-17D, there is shown an alternative compressor800 in accordance with the principles of the present disclosure. Thecompressor 800 includes a case body 802 that defines a chamber 806. Thecompressor 800 further includes within the chamber 806 a rotor assembly300 mounted on a shaft 302 and a ring piston 400 surrounding the rotorassembly 300. The rotor assembly 300 includes a set of roller bearings804 that are in contact with the inner surface of the ring piston 400 asthe rotor assembly rotates about a central axis extending through theshaft 302.

The compressor 800 further includes a pair of opposed compression vanes500. Each compression vane 500 includes a seal component 510 with asurface that matches the outer curvature of the ring piston 400 to forma continuous surface seal between the seal component 510 and the ringpiston 400 as the rotor assembly 300 and the ring piston 400 rotateabout the axis of the shaft 302, the position of the continuous surfaceseals in the chamber 806 defining a first sub-chamber and a secondsub-chamber between the surface seals. Each compression vane 500 alsoincludes a spring 512 that urges the vane 500 towards the ring piston400 to maintain a seal between the seal component 510 and the ringpiston 400.

Associated with each sub-chamber of the chamber 806 is an exhaust portassembly 600 and an inlet port assembly 700. In various implementations,a pair of exhaust port assemblies 600 are positioned diametricallyopposed to each other, and a pair of inlet port assemblies 700 arepositioned diametrically opposed to each other. Each exhaust portassembly 600 includes an inlet opening 608, and each inlet port assembly700 includes an outlet opening 708.

The compressor 800 also includes one or more mounting sites 803. Themounting sites 803 enable the compressor 800 to any suitable structure.Kinetic input energy is provided by the rotation of the shaft 302. Thecompressor case body 802 is made from metallic, ceramic syntheticmaterial, or any other suitable material.

Referring further to FIG. 17E, there is shown two or more staged orstacked compressors 800 mounted about the shaft 302. In someimplementations, for example, in a two-stage configuration, the secondunit is offset from the first unit by 90°, and in a three-stageconfiguration, the second unit is offset from the first unit by 120° andthe third unit is offset from the first unit by 240°. In variousimplementations, a plate 805 positioned on the outer surfaces of theouter most compressors 800. In certain implementations a plate 805 ispositioned between the compressors 800.

In various implementations, the configuration shown in FIG. 17E producesmaximum compressor fluid flow or maximum air pressure for a givenrotational speed of the shaft 302, depending on how the inlets 608 andthe outlets 708 are connected together. The configuration is utilized incertain implementations as an air motor optimized for an input of highair flow rate at low pressure or low air flow rate at high pressure. Theconfiguration can also be operated with both motors and compressorsmounted about a single shaft 302. As such, the configuration can utilizekinetic, pneumatic or hydraulic energy input to generate pneumatic orhydraulic output, as well as kinetic output.

In various implementations, the one or more compressors 800 operateunder various thermal and pressure cycle environments. For example, thecompressor 800, can be utilized, but not limited to, hazardous explosiveenvironments, clean room environments where the risk of particulates maybe harmful, and laboratory and medical theatre environments whereantiseptic and antimicrobial matter is maintained at extreme levels.

In some implementations, the compressor 800 features adjustableeccentric bearing shafts on the rotary piston ring 400 drive bearings805 that permit the eccentricity of the rotary piston ring 400 to bemicro-adjusted to enable the precise control of the clearance betweenthe rotary piston ring 400 and chamber 806 of the case body 802. Thisadjustability permits optimized performance and efficiency of thecompressor 800.

Low friction, dry sliding, bearing plates 808 made from nano-particlematerial protect the oscillating motion of the sliding compression vanes500 from friction and wear. These bearing plates permit lubrication-freeoperation and protect the oscillating motion of the sliding vanes 500.The compressor 800 utilizes pressure balance porting, through or aroundthe slide vanes 500, which applies pressure and a resulting force to theslide vane 500 which keeps seal components 510 in contact with therotary piston ring 400. Pressure balance features in the face of theseal components 510 balance the pressure on the seal components 510 torotary piston ring 400 interface to minimize drag and resultingmechanical losses while maintaining the sealing function. Further,externally attached, modular check valve housings, with common inlet 708and outlet 608 interfaces, permit easy reconfiguration from compressorto motor operation, and easy change from clockwise to counter-clockwiserotation of the shaft 302. Device architecture is scalable to allowoptimization of individual stages sizes, number of stages, andcombination of stages configurations for a broad spectrum of specificapplications.

Referring now to FIGS. 12A through 12C, there are shown further detailsof the rotor assembly 300. The rotor assembly 300 includes concentricbearing mounting flanges 304, 306, 308 and 314 that define mountingslots 307 and 310 to mount, for example, roller bearings 805. Note thatthe present disclosure is not limited to the use of two bearings on eachbearing shaft. Specific design geometries and configurations as depictedare scalable, depending on the overall system performance requirementsand specifications. The rotor mass 312 is configured to provideinternally-balanced operation. The internally-balanced rotating mass 312of the eccentric hub results in minimal rotational vibration andimproved bearing compressor life. This balanced mass also permits thejoining of multiple compressor and motor stages on a single rotationalaxis without the use of external balancing devices. The output shaft 302is keyed for multiple connections to other compressors as illustrated inFIG. 17E and to interface with other external system components. Forexample, the shaft 302 can interface with other features including, butnot limited to, splines, geometric shapes (such as hexagonal shapes),pinned connectors and smooth shafts.

Turning now to FIGS. 13A through 13C, there are shown further details ofthe rotary ring piston 400. The ring piston 400 includes an outersurface 402 that interfaces with the seal components 510 of thecompression vanes 500. The ring piston 400 has bearing races 406 on theinside of the ring piston 400. Additional bearing races can be added tothe ring piston 400 to correspond to the number of bearing utilized bythe rotor assembly 300 positioned in an opening 404. The outer surface402 and inner surfaces 404 and 406 are coated with a material made ofnano-particles in various implementations to provide lubrication-lessoperation of the ring piston 400. The piston ring 400 is sealed via asealing material in slots 403 on the outer circumference of on both sideof the piston ring 400. The piston ring can be made from a variety ofmaterials including metallic, ceramic, and synthetic materials. Thesealing material 403 is dry-sliding, low friction, ring insets in theend face of the rotary piston ring 400 in various implementations thatact as both a seal and a bearing surface. This maintains a mean pressureregion inside the rotary piston ring 400 that reduces the internalleakage from the compression space, resulting in greater compressionperformance.

Referring now to FIGS. 14A and 14B, there are shown further details ofthe compression vane 500. The compression vane 500 is configured withgeometries 502 and 504 to ensure desired sealing between the compressionvane and the case body 802 of the compressor 800. For example, sealcomponents, such as, for example, seal component 510 is utilized invarious implementations. The compression vane 500 also includes channels510 and 512 and balancing ports 508 and 514 to provide dynamic positivepressure to maintained aligned operand of the seal component 510 to theouter surface 402 of the piston ring 400. The body of the compressionvane 500 can be made from a variety of metallic, ceramic or syntheticmaterials.

Referring now to FIGS. 15A to 15D, there are shown further details ofthe exhaust port assembly 600. The exhaust port assembly 600 includes afirst portion 602 and a second portion 604 joined together with a set offasteners 612. The exhaust port assembly 600 is modular to provide rapidreconfiguration on the compressor 800. In some implementations, theexhaust port assembly 600 satisfies ISO standards. The exhaust portassembly 600 utilizes a check valve based on a reed valve 614. The readvalve has one end 615 attached to the portion 604 with a fastener 616.The exhaust port assembly 600 further includes an interface slot 610that communicates with a respective sub-chamber of the chamber 806 andan exhaust port 606 with an opening 608. Accordingly, a fluid at adesired pressure pushes an end 617 of the reed valve 614 away from theinterface slot 610 so that fluid drawn from a respective sub-chamber ofthe chamber 806 into the exhaust port assembly 600 and is exhausted fromthe exhaust port assembly 600 through the opening 608. The body of theexhaust port assembly can be made from a variety of metallic, ceramic orsynthetic materials.

Referring now to FIGS. 16A to 6D, there are shown further details of theinlet port assembly 700. The inlet port assembly 700 includes a firstportion 702 and a second portion 704 joined together with a set offasteners 710. The inlet port assembly 700 is modular to provide rapidreconfiguration on the compressor 800. In some implementations, theinlet port assembly 700 satisfies ISO standards. The inlet port assembly700 utilizes a check valve based on a reed valve 718. The read valve hasone end 720 attached to the portion 702 with a fastener 722. The inletport assembly 700 further includes an interface 712 with a slot 714 thatcommunicates with a respective sub-chamber of the chamber 806 and aninlet port 706 with an opening 708. Accordingly, a fluid at a desiredpressure pushes an end 724 of the reed valve 718 away from a slottedopening 716 that is in fluid communication with the opening 708 so thatfluid is drawn into the opening 708 and exits the inlet port assembly700 through the slot 714 into a respective sub-chamber of the chamber806. The body of the exhaust port assembly can be made from a variety ofmetallic, ceramic or synthetic materials.

Both the exhaust port assembly 600 and the inlet port assembly utilizecheck valves based on reed valves that are configured to minimizepressure losses, facilitate rapid checking (that is, sealing) for highspeed operation, and for long life.

The description of the present disclosure is merely exemplary in natureand variations that do not depart from the gist of the presentdisclosure are intended to be within the scope of the presentdisclosure. Such variations are not to be regarded as a departure fromthe spirit and scope of the present disclosure.

What is claimed is:
 1. A compressor comprising: an assembly with a casebody defining a chamber; a shaft defining a rotational axis; a ringpiston positioned within the chamber; a rotor assembly positioned withinthe ring piston, the rotor assembly being mounted on the shaft; and apair of opposed compression vanes, each compression vane having a sealcomponent with a surface that matches an outer curvature of the ringpiston to form a continuous surface seal between the seal component andthe ring piston as the rotor assembly and the ring piston rotate aboutthe axis of the shaft, the position of the continuous surface seals inthe chamber defining a first sub-chamber and a second sub-chamberbetween the surface seals, the case body further including an inlet portand an exhaust port for each sub-chamber.
 2. The compressor of claim 1,wherein the compressor is configured to be staged with one or moreadditional compressors on the shaft.
 3. The compressor of claim 2,wherein the staged compressors provide maximum fluid flow or maximumflow pressure depending upon the of the arrangement of the connectionsbetween the inlet ports and the outlet ports.
 4. The compressor of claim2, wherein the staged compressors are configured to operate as an airmotor for an input of high air flow rate at low pressure or low air flowrate at high pressure.
 5. The compressor of claim 2, wherein the stagedcompressors operate as both motors and compressors on the singlerotational axis defined by the shaft to utilize a kinetic, pneumatic orhydraulic energy source to generate a pneumatic or hydraulic output, aswell as a kinetic output.
 6. The compressor of claim 1, wherein theinlet port is defined by an assembly including a check valve.
 7. Thecompressor of claim 6, wherein the check valve is a reed valve made of athin, flexible material.
 8. The compressor of claim 1, wherein theoutlet port is defined by an assembly including a check valve.
 9. Thecompressor of claim 8, wherein the check valve is a reed valve made of athin, flexible material.
 10. The compressor of claim 1, wherein an innersurface or an outer surface or both the inner surface and the outersurface of the ring piston are coated with a material made ofnano-particles to provide lubrication-less operation of the compressor.11. An assembly with a plurality of compressors, each compressorcomprising: an assembly with a case body defining a chamber; a shaftdefining a rotational axis; a ring piston positioned within the chamber;a rotor assembly positioned within the ring piston, the rotor assemblybeing mounted on the shaft; and a pair of opposed compression vanes,each compression vane having a seal component with a surface thatmatches an outer curvature of the ring piston to form a continuoussurface seal between the seal component and the ring piston as the rotorassembly and the ring piston rotate about the axis of the shaft, theposition of the continuous surface seals in the chamber defining a firstsub-chamber and a second sub-chamber between the surface seals, the casebody further including an inlet port and an exhaust port for eachsub-chamber, wherein the compressors are configured to be staged withone or more additional compressors on the shaft to rotate about therotational axis.
 12. The assembly of claim 11, wherein the stagedcompressors are configured to operate as an air motor for an input ofhigh air flow rate at low pressure or low air flow rate at highpressure.
 13. The compressor of claim 11, wherein the staged compressorsoperate as both motors and compressors on the single rotational axisdefined by the shaft to utilize a kinetic, pneumatic or hydraulic energysource to generate a pneumatic or hydraulic output, as well as a kineticoutput.
 14. The assembly of claim 11, wherein the inlet port is definedby an inlet assembly including a check valve.
 15. The assembly of claim14, wherein the check valve is a reed valve made of a thin, flexiblematerial.
 16. The assembly claim 11, wherein the outlet port is definedby an outlet assembly including a check valve.
 17. The assembly of claim16, wherein the check valve is a reed valve made of a thin, flexiblematerial.
 18. The assembly of claim 11, wherein an inner surface or anouter surface or both the inner surface and the outer surface of thering piston are coated with a material made of nano-particles to providelubrication-less operation of the compressor.